Secondary burner

Details Secondary burner Secondary burner

F - Mech Eng,Light,Heat,Weapons

02

M

F02M 25/08 (2006.01) F23M 99/00 (2010.01) F23R 3/28 (2006.01) F23M 13/00 (2006.01)

Patent

CA 2098810

92/078 ABSTRACT OF THE DISCLOSURE In a secondary burner for a gas turbine combustion chamber, a fuel feed (2, 3) arranged in a combustion chamber wall (1) is surrounded by an annular air duct (4). The air duct (4) communicates, by means of at least one supply tube (5), with a through-flow Helmholtz resonator (6). The outlet from the Helmholtz resonator damping tube (7), which is configured as an annular duct, is located in the region of the burner mouth (8) in the secondary combustion space (9). (Fig. 1)

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